EP1862605A2 - Enceinte thermo-acoustique - Google Patents

Enceinte thermo-acoustique Download PDF

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Publication number
EP1862605A2
EP1862605A2 EP07108989A EP07108989A EP1862605A2 EP 1862605 A2 EP1862605 A2 EP 1862605A2 EP 07108989 A EP07108989 A EP 07108989A EP 07108989 A EP07108989 A EP 07108989A EP 1862605 A2 EP1862605 A2 EP 1862605A2
Authority
EP
European Patent Office
Prior art keywords
panel
enclosure
wall
inner panel
stiffening members
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07108989A
Other languages
German (de)
English (en)
Other versions
EP1862605A3 (fr
EP1862605B1 (fr
Inventor
Stephen Craig Mitchell
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1862605A2 publication Critical patent/EP1862605A2/fr
Publication of EP1862605A3 publication Critical patent/EP1862605A3/fr
Application granted granted Critical
Publication of EP1862605B1 publication Critical patent/EP1862605B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
    • E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
    • E04B1/62—Insulation or other protection; Elements or use of specified material therefor
    • E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
    • E04B1/82—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only
    • E04B1/8218—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only soundproof enclosures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G13/00—Other offensive or defensive arrangements on vessels; Vessels characterised thereby
    • B63G13/02—Camouflage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H21/00—Use of propulsion power plant or units on vessels
    • B63H21/12—Use of propulsion power plant or units on vessels the vessels being motor-driven
    • B63H21/16—Use of propulsion power plant or units on vessels the vessels being motor-driven relating to gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • This invention relates generally to enclosures for apparatus that, during operation, generates heat and sound energy. More particularly, it relates to an enclosure for a turbine engine used for such applications as marine or industrial.
  • Gas turbine engines used to generate power in marine or industrial applications are required to be contained or packaged in an enclosure to reduce levels of noise or sound energy and heat generated during engine operation, as well as to provide fire protection.
  • existing designs of such enclosures include heavy metal structures based on the theory that mass is the primary factor in sound attenuation and therefore increased mass results in increased sound attenuation or transmission loss.
  • the walls of current enclosures include heavy, solid and porous metal plates with a large number of stiffening beams to achieve a desired sound frequency attenuation. Damping compound is added to provide damping of acoustic energy and reduce heat transmission. The result is a relatively heavy acoustic enclosure.
  • a method for assembling a gas turbine engine assembly includes coupling a first wall, a second wall, a third wall, and a fourth wall together to form an enclosure, at least one of the first, second, third, or fourth walls including a first panel including an inner layer, an outer layer, and a plurality of spaced-apart transverse walls between the inner and outer layers, and a second panel that includes at least an outer layer and a first acoustic material, the first panel coupled to the second panel such that the outer surface of the first panel is flush against the outer surface of the second panel, and positioning a gas turbine engine within the enclosure such that at least a portion of the gas turbine engine is contained within the enclosure.
  • an enclosure for an apparatus having at least one wall defining at least a portion of an enclosure hollow interior includes an inner panel comprising, in sequence outwardly from the enclosure hollow interior, an inner sheet comprising a plurality of perforations extending therethrough, a plurality of panel stiffening members coupled to the inner sheet, and at least one inner panel sound absorption member comprising non-metallic sound absorption material positioned between adjacent of the plurality of panel stiffening members, and an outer panel comprising in sequence inwardly from outside of the enclosure, an outer panel sandwich member comprising non-metallic composite material including spaced-apart first and second walls and a plurality of spaced-apart transverse walls extending between the first and second walls defining hollow chambers therebetween, the outer panel coupled to the inner panel such that an outer surface of the inner panel is substantially flush against an outer surface of the outer panel.
  • a gas turbine engine assembly in a further aspect, includes an enclosure including a first wall, a second wall, a third wall, and a fourth wall.
  • Each wall includes an inner panel comprising, in sequence outwardly from the enclosure hollow interior, an inner sheet comprising a plurality of perforations extending therethrough, a plurality of panel stiffening members coupled to the inner sheet, and at least one inner panel sound absorption member comprising non-metallic sound absorption material positioned between adjacent of the plurality of panel stiffening members, and an outer panel comprising in sequence inwardly from outside of the enclosure, an outer panel sandwich member comprising non-metallic composite material including spaced-apart first and second walls and a plurality of spaced-apart transverse walls extending between the first and second walls defining hollow chambers therebetween, the outer panel coupled to the inner panel such that an outer surface of the inner panel is substantially flush against an outer surface of the outer panel, and a gas turbine engine positioned within the enclosure.
  • Wall 2 includes, in sequence from outside 3 of enclosure wall 2, a heavy metal plate 4, a sprayed-on thick rubber coating material 5, felt batting material 6 (typically including a thin film facing 7) to provide damping of acoustic energy, and a perforated metal face sheet 8 (including pores 9 therethrough) adjacent enclosure inside or enclosure hollow interior 10.
  • Supporting such prior art structure is a large number of heavy metal stiffening beams (not shown).
  • Such current design results in a relatively heavy structure for an enclosure in order to satisfy specified sound energy attenuation requirements.
  • Various embodiments of the present invention eliminate heavy metal walls and supports by including wall components that are fabricated utilizing primarily non-metallic composite materials, including fiber reinforced composites, to provide high damping and stiffness characteristics to the wall.
  • a lighter weight support frame can be used to provide a structurally strong, yet lightweight, enclosure that includes enhanced acoustic characteristics and reduced heat transfer through enclosure walls, along with fire protection and in-plane shear loading capabilities.
  • FIG. 2 is a schematic illustration of an exemplary gas turbine engine 11 including an inlet portion 12, an engine portion 14, and an exhaust portion 16.
  • Engine portion 14 includes at least one compressor 18, a combustor 20, a high pressure turbine 22, and a low pressure turbine 24 connected serially.
  • Inlet portion 12 includes an inlet 26, and exhaust portion 16 includes an exhaust nozzle 28.
  • engine 11 is an LM2500 engine commercially available from General Electric Company, Cincinnati, Ohio.
  • Compressor 18 and turbine 22 are coupled by a first shaft 30, and turbine 24 and a driven load 32 are coupled by a second shaft 34.
  • FIG. 3 is a perspective view of an exemplary module assembly 36.
  • module assembly 36 may be used to enclose any gas turbine engine, in the exemplary embodiment module assembly 36 is used to enclose gas turbine engine 11.
  • module assembly 36 includes a first wall 40, a second wall 42 that is coupled to first wall 40, a third wall 44 that is coupled to second wall 42, and a fourth wall 46 that is coupled to third wall 44 and first wall 40 such that module assembly 36 defines an approximately rectangular enclosure that is suitably sized to enclose engine assembly 11. More specifically, first wall 40 is substantially parallel to third wall 44 and also substantially perpendicular to second and fourth walls 42 and 46, respectively and second wall 42 is substantially parallel to fourth wall 46 and substantially perpendicular to first and third walls 40 and 44, respectively.
  • module assembly 36 also includes a ceiling 48 and a floor 50 that are each coupled to an upper or lower surface of first, second, third, and fourth walls 40, 42, 44, and 46, respectively such that engine assembly 11 is completely enclosed within module assembly 36.
  • FIGmatic, perspective, fragmentary, partially sectional view of Figure 4 and the diagrammatic, fragmentary, partially sectional plan view of Figure 5 along lines 5 - 5 of Figure 4 represents an enclosure wall, shown generally as wall 40 according to an embodiment of the present invention. Although the invention is described with respect to wall 40, it should be realized that walls 42, 44, 46, ceiling 48 or floor 50 may be fabricated using the methods and apparatus described below.
  • Wall 40 includes an inner panel shown generally at 60 and an outer panel shown generally at 62.
  • Inner panel 60 includes, in sequence outwardly from enclosure hollow interior 10, an inner panel inner sheet 70, typically of a metal such as steel, at hollow interior 10 and including a plurality of perforations 72 therethrough.
  • an inner panel sound absorption member 74 substantially made of commercially available non-metallic sound absorption material, for example a polymeric foam or porous material such as is currently made of such materials as polyurethane, rockwool, phenolic, melamine, etc.
  • member 74 is shown to include a plurality of layers that can be of the same or different materials as desired for sound attenuation.
  • member 74 includes a thin film facing 76, for example of a metallized polymeric material.
  • Inner panel 60 further includes an inner panel outer sheet 78 substantially made of a non-metallic material, for example of a fiber reinforced resin matrix.
  • inner panel 60 also includes a plurality of panel stiffening members 82 that are coupled between inner panel inner sheet 70 and inner panel outer sheet 78.
  • each stiffening member 82 is an I-shaped beam that is fabricated from a relatively light-weight composite or metallic material.
  • each stiffening member 82 is made substantially of a non-metallic composite material, for example fiber reinforced, to provide a combination of lightweight and strength to wall 40.
  • each stiffening member 82 may form generally a "C" shaped channel about sound absorption member 74, although other shapes such as a "Z" shaped channel can be used.
  • inner panel fastening means shown generally at 84, for example shown as typical bolts, studs, nuts, spacers, and pressure plates.
  • fastening means can include interface bonding or adhesive type materials.
  • Fastening means 84 are provided to hold the inner panel inner sheet 70, sound absorption material 74, and inner panel outer sheet 78 in sequence, and to hold stiffening members 82 within inner panel 60.
  • Outer panel 62 includes, in sequence inwardly from outside 3 of enclosure 36, outer panel sandwich member shown generally at 90 substantially made of a non-metallic composite material, preferably fiber reinforced for enhanced stiffness.
  • Sandwich member 90 includes spaced-apart sandwich member first and second walls 92 and 94, respectively, and a plurality of spaced-apart transverse walls 96 therebetween that define a plurality of hollow chambers 98 therebetween.
  • outer panel 62 also includes a plurality of heat, fire resistant, and/or sound absorption cores 100 that are positioned between inner and outer walls 92 and 94 respectively. More specifically, each core 100 is positioned between spaced apart transverse walls 96 within a respective hollow chamber 98.
  • outer panel 62 does not include cores 100.
  • each core 100 is fabricated using a commercially available non-metallic material, for example a polymeric foam or porous material such as is currently made of such materials as polyurethane, rockwool, phenolic, melamine, etc.
  • inner panel 60 is coupled to outer panel 62 using fasteners 84.
  • inner panel 60 is coupled to outer panel 62 such that the outer surface of inner panel sound absorption member 74 is flush against the outer surface of second panel second wall 92. That is the exterior surface of inner panel 60 is in contact with, or flush to, the exterior surface of outer panel 62.
  • inner panel outer sheet 78 is inserted between panels 60 and 62 to further increase the structural stiffness of the walls and/or to facilitate decreasing noise transmission through the walls.
  • Described herein is a relatively lightweight enclosure wall that integrates three separate optimized structural elements into one unitized structure. Moreover the enclosure wall has improved acoustic and structural capabilities compared to known enclosure walls. For example, during operation, sound radiating from the gas turbine engine first strikes the surface of the inner panel structure that includes a perforated or solid face sheet backed with a multilayer acoustic absorptive sheet. The multilayer acoustic absorptive sheet may also be subdivided by stiffeners into horizontal or vertical chambers. As such, the inner panel provides acoustic absorptive and transmission loss characteristics.
  • the enclosure wall also includes an internal skeletal structure that is fabricated utilizing a plurality of beams that acoustically isolate the inner and outer panels, and also provide the primary structural support of the enclosure.
  • the inner and outer panels are fastened to the beams with either mechanical isolation fasteners or bonded with sealants or adhesives.
  • the outer panel provides acoustic transmission loss characteristics, reduced heat flow, fire protection plus in-plane shear loading capabilities.
  • the outer panel is fabricated as a sandwich-like structure that includes a pair of composite facesheets that are separated by a medium such as foam or honeycomb, for example.
  • the facesheets are connected by both foam and rib stiffeners.
  • the channels between the ribs may be hollow, filled with foam or other sound absorbing media.
  • the high damping and stiffness characteristics of the composite material and sandwich construction facilitate providing an efficient lightweight transmission loss structure.
  • the wall structure may include a relatively thin metallic plate that is coupled to the outer panel to further increase the transmission loss and also provide fire protection and external damage protection.
  • the low transverse thermal conductivity of composites coupled with the sandwich panel facilitate reducing heat flow and also provides relatively low exterior temperatures.
  • the enclosure wall described herein facilitates reducing the overall weight of the engine module structure, provides improved acoustic characteristics, and also reduces outside wall temperatures and fire protection compared to known enclosure walls.
  • the present invention provides an enclosure with a significantly improved combination of reduced weight and structural stability along with sound loss characteristics and heat and fire resistance through the arrangement and use primarily of non-metallic materials.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Acoustics & Sound (AREA)
  • Architecture (AREA)
  • Electromagnetism (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ocean & Marine Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Building Environments (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
EP07108989.0A 2006-06-01 2007-05-25 Enceinte thermo-acoustique Expired - Fee Related EP1862605B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/444,659 US7604095B2 (en) 2006-06-01 2006-06-01 Thermal-acoustic enclosure

Publications (3)

Publication Number Publication Date
EP1862605A2 true EP1862605A2 (fr) 2007-12-05
EP1862605A3 EP1862605A3 (fr) 2012-04-11
EP1862605B1 EP1862605B1 (fr) 2014-03-05

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Family Applications (1)

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EP07108989.0A Expired - Fee Related EP1862605B1 (fr) 2006-06-01 2007-05-25 Enceinte thermo-acoustique

Country Status (4)

Country Link
US (1) US7604095B2 (fr)
EP (1) EP1862605B1 (fr)
JP (1) JP5237583B2 (fr)
CA (1) CA2590081C (fr)

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EP2821621A1 (fr) * 2013-07-03 2015-01-07 Pratt & Whitney Canada Corp. Structure acoustique pour un moteur à turbine à gaz
ITUB20160493A1 (it) * 2016-01-29 2017-07-29 Nuovo Pignone Tecnologie Srl Pannello multistrato per installazioni di macchinari

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2821621A1 (fr) * 2013-07-03 2015-01-07 Pratt & Whitney Canada Corp. Structure acoustique pour un moteur à turbine à gaz
US9909501B2 (en) 2013-07-03 2018-03-06 Pratt & Whitney Canada Corp. Acoustic structure for a gas turbine engine
ITUB20160493A1 (it) * 2016-01-29 2017-07-29 Nuovo Pignone Tecnologie Srl Pannello multistrato per installazioni di macchinari
WO2017129696A1 (fr) * 2016-01-29 2017-08-03 Nuovo Pignone Tecnologie Srl Panneau multicouche pour une enceinte de machines
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US11473297B2 (en) 2016-01-29 2022-10-18 Nuovo Pignone Tecnologie Srl Multilayered panel for machinery enclosure

Also Published As

Publication number Publication date
CA2590081A1 (fr) 2007-12-01
CA2590081C (fr) 2015-03-24
US7604095B2 (en) 2009-10-20
EP1862605A3 (fr) 2012-04-11
EP1862605B1 (fr) 2014-03-05
US20070278035A1 (en) 2007-12-06
JP2007321761A (ja) 2007-12-13
JP5237583B2 (ja) 2013-07-17

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